U.S. patent application number 11/477373 was filed with the patent office on 2008-01-03 for power system.
This patent application is currently assigned to Solar Turbines Incorporated. Invention is credited to Ian Trevor Brown, Daniel James Doll.
Application Number | 20080003093 11/477373 |
Document ID | / |
Family ID | 38876841 |
Filed Date | 2008-01-03 |
United States Patent
Application |
20080003093 |
Kind Code |
A1 |
Brown; Ian Trevor ; et
al. |
January 3, 2008 |
Power system
Abstract
A power system includes a gas turbine engine. The gas turbine
engine may include a first portion, a second portion, and a
longitudinal axis. The power system may also include a first
moveable support engaged to the first portion of the gas turbine
engine. The first moveable support may be operable to at least
partially constrain movement of the first portion of the gas
turbine engine during operation of the gas turbine engine.
Additionally, the first moveable support may be operable to at
least partially support the first portion of the gas turbine engine
as the first portion of the gas turbine engine is moved away from
the longitudinal axis independently of the second portion of the
gas turbine engine.
Inventors: |
Brown; Ian Trevor; (San
Diego, CA) ; Doll; Daniel James; (Poway, CA) |
Correspondence
Address: |
CATERPILLAR/FINNEGAN, HENDERSON, L.L.P.
901 New York Avenue, NW
WASHINGTON
DC
20001-4413
US
|
Assignee: |
Solar Turbines Incorporated
|
Family ID: |
38876841 |
Appl. No.: |
11/477373 |
Filed: |
June 30, 2006 |
Current U.S.
Class: |
415/1 |
Current CPC
Class: |
Y10T 29/49895 20150115;
Y10T 29/49998 20150115; F16M 5/00 20130101; F02C 7/20 20130101;
F05D 2230/60 20130101; Y10T 29/53961 20150115; Y10T 29/53548
20150115; F16M 1/04 20130101 |
Class at
Publication: |
415/1 |
International
Class: |
F04D 27/02 20060101
F04D027/02 |
Claims
1. A power system, including: a gas turbine engine, the gas turbine
engine including a first portion, a second portion, and a
longitudinal axis; a first moveable support engaged to the first
portion of the gas turbine engine, the first moveable support being
operable to at least partially constrain movement of the first
portion of the gas turbine engine during operation of the gas
turbine engine; and at least partially support the first portion of
the gas turbine engine as the first portion of the gas turbine
engine is moved away from the longitudinal axis independently of
the second portion of the gas turbine engine.
2. The power system of claim 1, wherein the first moveable support
is operable to substantially fully support the first portion of the
gas turbine engine as the first portion of the gas turbine engine
is being moved away from the longitudinal axis independently of the
second portion of the gas turbine engine.
3. The power system of claim 1, further including: a second support
that at least partially supports the first moveable support; and
wherein the first moveable support is operable to slide with
respect to the second support when at least partially supporting
the first portion of the gas turbine engine as the first portion of
the gas turbine engine moves away from the longitudinal axis.
4. The power system of claim 1, wherein the first moveable support
is operable to slide off of the second support while at least
partially supporting the first portion of the gas turbine
engine.
5. The power system of claim 1, further including at least one
guide operable to direct movement of the first moveable
support.
6. The power system of claim 1, further including a second moveable
support operable to at least partially support the second portion
of the gas turbine engine while the second portion of the gas
turbine engine is moved at least partially in the direction of the
longitudinal axis independently of the first portion of the gas
turbine engine.
7. The power system of claim 1, further including: a second support
engaged to the second portion of the gas turbine engine; wherein
the first moveable support and the second moveable support are
parts of a frame configured to substantially fully support the
first portion of the gas turbine engine and the second portion of
the gas turbine engine in substantially fixed relative positions
when the first moveable support and the second moveable support are
fastened in substantially fixed positions with respect to one
another.
8. The power system of claim 7, further including: a power load
drivingly connected to the gas turbine engine; and a common base
supporting the power load and the frame.
9. A method of using a power system, including: selectively
operating a gas turbine engine to produce power; while operating
the gas turbine engine to produce power, constraining movement of
the gas turbine engine, including at least partially constraining
movement of a first portion of the gas turbine engine with a first
moveable support; and when not operating the gas turbine engine to
produce power, selectively moving the first portion of the gas
turbine engine away from a longitudinal axis of the gas turbine
engine independently of a second portion of the gas turbine engine
while at least partially supporting the first portion of the gas
turbine engine with the first moveable support.
10. The method of claim 9, wherein constraining movement of the gas
turbine engine when operating the gas turbine engine to produce
power includes substantially fully supporting the first portion of
the gas turbine engine and the second portion of the gas turbine
engine with a frame that includes the first moveable support and a
second support engaged to the second portion of the gas turbine
engine.
11. The method of claim 10, further including: while operating the
gas turbine engine to produce power, driving a power load with the
gas turbine engine; and while driving the power load with the gas
turbine engine, supporting the power load and the frame with a
common base.
12. The method of claim 11, further including: when not operating
the gas turbine engine to produce power, selectively disconnecting
the gas turbine engine from the power load and removing the frame,
the first portion of the gas turbine engine, and the second portion
of the gas turbine engine from the base as a unit.
13. The method of claim 9, wherein: at least partially constraining
movement of the first portion of the gas turbine engine with the
first moveable support when operating the gas turbine engine to
produce power includes supporting the first moveable support on a
second support; and selectively moving the first portion of the gas
turbine engine away from the longitudinal axis of the gas turbine
engine independently of the second portion of the gas turbine
engine while at least partially supporting the first portion of the
gas turbine engine with the first moveable support includes
selectively sliding the first moveable support off of the second
support while at least partially supporting the first portion of
the gas turbine engine with the first moveable support.
14. The method of claim 9, wherein selectively moving the first
portion of the gas turbine engine away from the longitudinal axis
of the gas turbine engine independently of a second portion of the
gas turbine engine while at least partially supporting the first
portion of the gas turbine engine with the first moveable support
includes substantially fully supporting the first portion of the
gas turbine engine with the first moveable support.
15. The method of claim 9, further including: when not operating
the gas turbine engine to produce power, moving the second portion
of the gas turbine engine at least partially in the direction of
the longitudinal axis of the gas turbine engine, while at least
partially supporting the second portion of the gas turbine engine
with a second support.
16. A support system for a gas turbine engine, the gas turbine
engine having a first portion and a second portion, the support
system including: a base; a first support that is supported by the
base, the first support being operable to at least partially
support the first portion of the gas turbine engine; and a second
support that is supported by the base, the second support being
operable to at least partially constrain movement of the second
portion of the gas turbine engine during operation of the gas
turbine engine; and the second support also being operable to at
least partially support the second portion of the gas turbine
engine while the second portion of the gas turbine engine moves
relative to the first portion of the gas turbine engine, including
the second support being operable to at least partially support the
second portion of the gas turbine engine while sliding off of the
base.
17. The support system of claim 16, further including at least one
guide for directing movement of the second support.
18. The support system of claim 16, further including at least one
portable support operable to receive the second support as it
slides off of the base.
19. The support system of claim 16, wherein the first support and
the second support are part of a frame that is operable to fully
support the first portion of the gas turbine engine and the second
portion of the gas turbine engine in substantially fixed relative
positions when the first support and the second support are
fastened in substantially fixed relative positions.
20. The support system of claim 19, wherein: the frame is operable
to be fastened in a substantially fixed position with respect to
the base to substantially fully support the first portion of the
gas turbine engine and the second portion of the gas turbine engine
in substantially fixed positions with respect to the base; and the
frame is further operable, when not fastened in a substantially
fixed position with respect to the base, to substantially fully
support the first portion of the gas turbine engine and the second
portion of the gas turbine engine while sliding off of the first
support.
Description
TECHNICAL FIELD
[0001] The present disclosure relates to power systems and, more
particularly, to power systems having a gas turbine engine.
BACKGROUND
[0002] Many power systems include a gas turbine engine and a power
load, such as a pump, compressor, or electric generator, drivingly
connected to the gas turbine engine. Various configurations of
support systems are employed to support the gas turbine engine and
the power load of such power systems. In some such power systems,
the gas turbine engine and the power load are both attached through
fixed mounts to a common, stationary support structure.
[0003] Unfortunately, such a support structure may make replacing
or repairing the gas turbine engine difficult. Removing the gas
turbine engine from the stationary support structure may involve
unfastening the gas turbine engine from numerous fixed mounts,
which may require considerable time and effort. Additionally, after
the gas turbine engine is unfastened from the support structure,
removing the gas turbine engine from the support structure may
require using lifting equipment and exercising considerable care to
avoid colliding the gas turbine engine with other objects.
[0004] Additionally, many repair operations may involve separating
sections of the gas turbine engine from one another, which may
require removing the gas turbine engine from the support structure.
For example, replacing a damaged section of the gas turbine engine
may require removing the gas turbine engine from the support
structure, separating the damaged section from the other sections,
installing a replacement section, and reassembling the sections of
the gas turbine engine. When the gas turbine engine is off of its
support structure, supporting and maneuvering the heavy, unwieldy
sections of the gas turbine engine when separating and reassembling
them may be quite difficult.
[0005] U.S. Pat. No. 6,871,504 to Kuroki et al. ("the '504 patent")
shows a power system having a gas turbine engine mounted to a base
by sliders and rails. The power system of the '504 patent includes
a gas turbine engine, a reduction gear, a generator, and a starting
apparatus drivingly connected to each other and supported by a
common base. Sliders attached to the underside of the gas turbine
engine rest on rails attached to a top side of the base. The
sliders and rails disclosed by the '504 patent enable sliding the
gas turbine engine onto and off of the common base.
[0006] Although the '504 patent discloses sliders and rails that
allow sliding the gas turbine engine thereof onto and off of the
common base, certain disadvantages persist. For example, the power
system shown by the '504 patent does not include any provisions for
supporting and maneuvering different sections of the gas turbine
engine independently. Accordingly, separating sections of the gas
turbine from one another to repair the gas turbine, as well as
removing one or more sections of the gas turbine engine from the
common base separately from other sections, may be difficult and
time consuming.
[0007] The power system of the present disclosure solves one or
more of the problems set forth above.
SUMMARY OF THE INVENTION
[0008] One disclosed embodiment relates to a power system that
includes a gas turbine engine. The gas turbine engine may include a
first portion, a second portion, and a longitudinal axis. The power
system may also include a first moveable support engaged to the
first portion of the gas turbine engine. The first moveable support
may be operable to at least partially constrain movement of the
first portion of the gas turbine engine during operation of the gas
turbine engine. Additionally, the first moveable support may be
operable to at least partially support the first portion of the gas
turbine engine as the first portion of the gas turbine engine is
moved away from the longitudinal axis independently of the second
portion of the gas turbine engine.
[0009] Another embodiment relates to a method of operating a power
system, including selectively operating a gas turbine engine to
produce power. The method may also include constraining movement of
the gas turbine engine while operating the gas turbine engine to
produce power, which may include at least partially constraining
movement of a first portion of the gas turbine engine with a first
moveable support. Additionally, the method may include, when not
operating the gas turbine engine to produce power, selectively
moving the first portion of the gas turbine engine away from a
longitudinal axis of the gas turbine engine independently of a
second portion of the gas turbine engine while at least partially
supporting the first portion of the gas turbine engine with the
first moveable support.
[0010] A further embodiment relates to a support system for a gas
turbine engine, the gas turbine engine having a first portion and a
second portion. The support system may include a base, a first
support that is supported by the base, and a second support that is
supported by the base. The first support may be operable to at
least partially support the first portion of the gas turbine
engine. The second support may be operable to at least partially
constrain movement of the second portion of the gas turbine engine
during operation of the gas turbine engine. The second support may
also be operable to at least partially support the second portion
of the gas turbine engine while the second portion of the gas
turbine engine moves relative to the first portion of the gas
turbine engine, which may include the second support being operable
to at least partially support the second portion of the gas turbine
engine while sliding off of the base.
BRIEF DESCRIPTION OF THE DRAWINGS
[0011] FIG. 1A is a perspective view of a support system for a
power system;
[0012] FIG. 1B is a plan view of the support system shown in FIG.
1A;
[0013] FIG. 1C is a side view of the support system shown in FIG.
1A;
[0014] FIG. 1D is an end view of the support system shown in FIG.
1A;
[0015] FIG. 2A is a perspective view of a power system that
includes the support system shown in FIG. 1A, wherein the power
system is in a first state;
[0016] FIG. 2B is a plan view of the power system shown in FIG.
2A;
[0017] FIG. 2C is a side view of the power system shown in FIG.
2A;
[0018] FIG. 2D is an end view of the power system shown in FIG.
2A;
[0019] FIG. 3A is a side view of the power system shown in FIG. 2A,
wherein the power system is in a second state;
[0020] FIG. 3B is a side view of the power system shown in FIG. 3A,
wherein the power system is in a third state;
[0021] FIG. 4A is a plan view of the power system shown in FIG. 2A,
wherein the power system is in a fourth state;
[0022] FIG. 4B is a plan view of the power system shown in FIG. 2A,
wherein the power system is in a fifth state; and
[0023] FIG. 5 is a plan view of the power system shown in FIG. 2A,
wherein the power system is in a sixth state.
DETAILED DESCRIPTION
[0024] FIGS. 1A-1D illustrate one embodiment of a support system 10
for a power system having a gas turbine engine (not shown in FIGS.
1A-1D), support system 10 having a power-transfer unit 12 and a
power load 14 mounted thereon. Support system 10 may include a
base/support 16 that supports power-transfer unit 12 and power load
14. For example, as FIGS. 1A-1D show, base/support 16 may be a
frame. Base/support 16 may be supported by various entities,
including, but not limited to, the ground (not shown), one or more
structures supported by the ground (not shown), one or more
structures of a vehicle (not shown), and/or one or more structures
of a marine vessel (not shown).
[0025] Support system 10 may include various provisions for
supporting a gas turbine engine (not shown). For example, support
system 10 may include a frame 28 for supporting a gas turbine
engine from base/support 16. Frame 28 may include a support 30 and
a support 32 disposed adjacent one another. Support 30 and support
32 may include provisions (not shown) for fastening support 30 and
support 32 in fixed positions relative to one another. For example,
support 30 and support 32 may include corresponding bolt holes (not
shown) at an interface 34 between support 30 and support 32 for
fixedly fastening support 30 to support 32. When not fastened in
fixed positions with respect to one another, supports 30, 32 may be
able to move independently of one another.
[0026] In some embodiments, such as the embodiment shown in FIGS.
1A-1D, supports 30, 32 may be configured to slide with respect to
base/support 16. Base/support 16 may include guide tracks 42, 44,
46 extending parallel to an axis 48 (FIGS. 1A, 1B). As is best
shown in FIG. 1C, supports 30, 32 may be guided by rollers 36, 38,
40 disposed in guide tracks 42, 44, 46 on base/support 16.
[0027] Support system 10 may include various provisions (not shown)
for holding supports 30, 32 stationary on base/support 16 when
desired. For example, support system 10 may include one or more
jacks for raising supports 30, 32 until rollers 36, 38, 40 are
separated from guide tracks 42, 44, 46, one or more props for
supporting supports 30, 32 in such elevated positions, and
fasteners for fixing supports 30, 32 in such elevated positions.
Additionally, or alternatively, support system 10 may also include
various other provisions (not shown) for selectively securing
supports 30, 32 at various positions along axis 48, including, but
not limited to, clamps, detents, fasteners, stops, and
ratchets.
[0028] Support system 10 may also include provisions for supporting
support 30 and/or support 32 off of base/support 16. For example,
support system 10 may include portable supports 50, 52, 54
configured to hold supports 30, 32. As FIGS. 1A-1D show, portable
supports 50, 52, 54 may include guide tracks 56, 58, 60 configured
to receive rollers 36, 38, 40 of supports 30, 32.
[0029] Support system 10 may also include a moveable support 62 and
a moveable support 64. Moveable support 62 may be configured to
slide on base/support 16. As FIGS. 1A-1D show, moveable support 62
may be guided by rollers 66 disposed in guide tracks 68 on
base/support 16. Guide tracks 68 may extend parallel to an axis 70
(FIGS. 1A-1C), which may be disposed at an angle, such as 90
degrees, to axis 48. Moveable support 64 may be configured to slide
on support 32. Moveable support 64 may be guided by rollers 72
disposed in guide tracks 74 on support 32. Like guide tracks 68,
guide tracks 74 may extend parallel to axis 70. Support system 10
may also include various provisions (not shown) for selectively
securing moveable supports 62, 64 at various positions along axis
70, including, but not limited to, clamps, detents, fasteners,
stops, and ratchets.
[0030] Support system 10 is not limited to the configuration shown
in FIGS. 1A-1D. For example, base/support 16 may be a collection of
separate support structures supported by the ground, rather than a
frame. Additionally, rather than being parts of a common frame 28,
supports 30, 32 may be fully independent of one another.
Furthermore, support system 10 may include provisions other than
rollers 36, 38, 40 and guide tracks 42, 44, 46 for facilitating
movement of supports 30, 32. For example, support system 10 may
include other types of slider systems and/or various types of
moveable linkages for facilitating movement of supports 30, 32.
Furthermore, each of the components of support system 10 may have
various shapes other than those shown in FIGS. 1A-1D.
[0031] Power-transfer unit 12 may be any type of component
configured to receive power from a power source (not shown in FIGS.
1A-1D) and transmit that power to power load 14. Power-transfer
unit 12 may include an input shaft 76 for receiving power from a
power source, an output shaft 78 connected to power load 14, and
various components for transferring power from input shaft 76 to
output shaft 78. In some embodiments, power-transfer unit 12 may be
a speed-reduction unit configured to rotate output shaft 78 at a
slower speed than the power source connected to input shaft 76
rotates input shaft 76.
[0032] Power load 14 may be any type of component configured to
receive power from power-transfer unit 12 and perform one or more
tasks with that power. For example, power load 14 may be an
electric generator, a pump, or a compressor.
[0033] FIGS. 2A-2D show a power system 80 that includes support
system 10, power-transfer unit 12, power load 14, and a gas turbine
engine 82 mounted to support system 10. Gas turbine engine 82 may
include a gas producer 84, a combustor 86, a power-turbine section
88, and an exhaust collector 90 fixedly connected to one another.
Gas producer 84 may include intake ducting 85 and a compressor 87.
Support 32 may support gas producer 84, and support 30 may support
power-turbine section 88. A longitudinal axis 92 of gas turbine
engine 82 may extend substantially parallel to axis 70. As is best
seen in FIGS. 2B and 2C, gas turbine engine 82 may include an
output shaft 94 connected to input shaft 76 of power-transfer unit
12.
[0034] Mounting of gas turbine engine 82 to support system 10 is
not limited to the example shown in FIGS. 2A-2D. For example,
sections of gas turbine engine 82 other than power-turbine section
88 and gas producer 84 may mount to supports 30 and 32,
respectively.
INDUSTRIAL APPLICABILITY
[0035] Power system 80 and support system 10 thereof may have
application wherever power is required for performing one or more
tasks. Gas turbine engine 82 may be operated to drive input shaft
76 of power-transfer unit 12 and, thereby, drive power load 14 to
pump fluid, generate electricity, or do other work. While gas
turbine engine 82 is driving power load 14, support 30 and support
32 may be fastened in substantially fixed positions with respect to
one another and fixedly fastened to base/support 16 to hold the
various portions of gas turbine engine 82 in substantially fixed
positions with respect to base/support 16.
[0036] When gas turbine engine 82 is not being operated to drive
power load 14, support system 10 may be used to support various
portions of gas turbine engine 82 while they are moved for various
purposes, such as repair. For example, as FIG. 3A shows, moveable
supports 62, 64 may be used to support compressor 87 and combustor
86 while compressor 87 and combustor 86 are moved along
longitudinal axis 92 away from power-turbine section 88 and exhaust
collector 90. In order to allow this, moveable supports 62, 64 may
first be engaged to compressor 87 in a manner such that they may
fully support compressor 87 and combustor 86. Subsequently, any
connections between compressor 87 and support 32 may be released,
and combustor 86 may be unfastened from power-turbine section 88.
Additionally, compressor 87 may be disconnected from intake ducting
85 to allow compressor 87 to move along longitudinal axis 92 while
intake ducting 85 remains stationary. For example, in some
embodiments annular rings (not shown) connected between an outer
surface of compressor 87 and intake ducting 85 may be removed so
that compressor 87 may move through a center portion of intake
ducting 85.
[0037] Subsequently, moveable supports 62, 64 may be slid along
axis 70 on guide tracks 68, 74 to move compressor 87 and combustor
86 along longitudinal axis 92 away from power-turbine section 88.
Once gas producer 84 and combustor 86 are at a desired position
along axis 92, the positions of moveable supports 62, 64 may be
secured to secure the position of gas producer 84 and combustor
86.
[0038] As FIG. 3B shows, intake ducting 85 may be left connected to
compressor 87 and moved with compressor 87 and combustor 86 along
axis 92 while moveable supports 62, 64 support compressor 87,
intake ducting 85, and combustor 86. This may entail unfastening
any connections fixing intake ducting 85 to support 32, other
ductwork (not shown), and/or other components before sliding
moveable supports 62, 64 along axis 70.
[0039] Additionally, as FIGS. 4A and 4B show, support 30 may be
used to support power-turbine section 88 and exhaust collector 90
while they are moved away from longitudinal axis 92 independently
of gas producer 84 and combustor 86. In order to allow this, output
shaft 94 of gas turbine engine 82 may be disconnected from input
shaft 76 of power-transfer unit 12. Additionally, any engagements
fixing the position of support 30 with respect to support 32 and
base/support 16 may be released. Subsequently, support 30 may be
slid on guide tracks 42, 44 to move power-turbine section 88 and
exhaust collector 90 away from longitudinal axis 92. In some
embodiments, such as the embodiment shown in FIGS. 4A and 4B,
support 30 may fully support power-turbine section 88 and exhaust
collector 90 as they are moved away from longitudinal axis 92. As
support 30 is moved along axis 48, support 30 may begin to move off
of guide tracks 42, 44 onto guide tracks 56, 58 of portable
supports 50, 52. Once power-turbine section 88 and exhaust
collector 90 are in a desired position along axis 48, various
provisions may be used to fix the position of support 30,
power-turbine section 88, and exhaust collector 90 along axis
48.
[0040] As FIG. 5 shows, support system 10 may also be used to
support gas turbine engine 82 as a unit as it is moved along axis
48. In order to allow this, supports 30, 32 may be left fixedly
fastened to one another, output shaft 94 of gas turbine engine 82
may be disconnected from input shaft 76 of power-transfer unit 12,
and any engagements fixing the position of frame 28 with respect to
base/support 16 may be released. Frame 28 may then be slid along
guide tracks 42, 44, 46. As frame 28 moves along axis 48, it may
begin to move off of base/support 16 onto portable supports 50, 52,
54.
[0041] The above-discussed abilities may facilitate maintenance of
power system 80 in a number of ways, thereby helping keep power
system 80 available to do work a high percentage of the time.
Longitudinally separating sections of gas turbine engine 82 may
provide access to internal components for repair. In some cases,
longitudinally separating sections of gas turbine engine 82 may
also eliminate longitudinal overlap between components of the
separated sections so that one or more of the sections may be moved
away from longitudinal axis 92 independently of other sections. In
circumstances where gas turbine engine 82 has been separated
longitudinally, one or more sections of gas turbine engine 82 may
be moved away from longitudinal axis 92 to improve the access to
internal components. Alternatively, one or more sections of gas
turbine engine 82 may be moved away from longitudinal axis 92
independently of other sections to provide access to internal
components, without longitudinally separating gas turbine engine
82.
[0042] Additionally, the ability to move one or more sections of
gas turbine engine 82 away from longitudinal axis 92 independently
of other sections, may allow quickly and easily replacing one or
more sections of gas turbine engine 82, without replacing other
sections. For example, power-turbine section 88 and exhaust
collector 90 may be replaced, without replacing gas producer 84 and
combustor 86. To do so, support 30, power-turbine section 88, and
exhaust collector 90 may first be slid off of base/support 16 onto
portable supports 50, 52, while support 32, gas producer 84, and
combustor 86 are left on base/support 16. Subsequently, support 30,
power-turbine section 88, and exhaust collector 90 may be removed
from portable supports 50, 52, and a replacement support,
power-turbine section, and exhaust collector may be loaded onto
portable supports 50, 52 and slid into place on base/support
16.
[0043] Additionally, the disclosed embodiments allow quickly and
easily replacing gas turbine engine 82 as a unit. To do so, frame
28 and gas turbine engine 82 may first be slid off of base/support
16 onto portable supports 50, 52, 54 and then removed from portable
supports 50, 52, 54. Subsequently, a replacement frame and gas
turbine engine may be loaded onto portable supports 50, 52, 54, and
slid into place on base/support 16.
[0044] After gas turbine engine 82 or a section thereof is removed
from base/support 16, it may be transported to a convenient service
facility for repair. During transport and repair of gas turbine
engine 82 or a section thereof, frame 28 or a support 30, 32
thereof may serve as a transport frame. When frame 28 and gas
turbine engine 82 are separated from base/support 16, frame 28 may
serve as a transport frame fully supporting gas turbine engine 82
during various operations. For example, frame 28 may fully support
gas turbine engine 82 during operations such as loading gas turbine
engine 82 onto a vehicle, transporting gas turbine engine 82 with
the vehicle, unloading gas turbine engine 82 from the vehicle, and
repairing gas turbine engine 82. Similarly, when support 30, power
turbine unit 88, and exhaust collector 90 are separated from
base/support 16, gas producer 84, and combustor 86, support 30 may
serve as a transport frame fully supporting power turbine unit 88
and exhaust collector 90 during transport and repair.
[0045] Use of support system 10 is not limited to the examples
discussed above and shown in the figures. For example, in some
cases, support 30, power-turbine section 88, and exhaust collector
90 may be held stationary on base/support 16 while support 32 is
moved on guide tracks 44, 46 to move gas producer 84 and combustor
86 away from longitudinal axis 92. Additionally, gas turbine engine
82 may be separated at points other than between combustor 86 and
power-turbine section 88, such as between gas producer 84 and
combustor 86. Furthermore, gas turbine engine 82 and/or sections
thereof may be moved for reasons other than those discussed
above.
[0046] In addition to providing the advantages discussed above, by
utilizing guide tracks 42, 44, 46, 68, 74 to limit movement of
supports 30, 32, 62, 64 to predetermined paths, the disclosed
embodiments allow precisely controlling the movement of gas turbine
engine 82 and sections thereof. This may help prevent collisions
when maneuvering gas turbine engine 82 and/or components thereof.
It may also facilitate achieving proper alignment between
components when assembling them to one another. These benefits may
be particularly significant under harsh conditions, such as in
adverse weather in a marine environment.
[0047] It will be apparent to those skilled in the art that various
modifications and variations can be made in the power system and
methods without departing from the scope of the disclosure. Other
embodiments of the disclosed power system and methods will be
apparent to those skilled in the art from consideration of the
specification and practice of the power system and methods
disclosed herein. It is intended that the specification and
examples be considered as exemplary only, with a true scope of the
disclosure being indicated by the following claims and their
equivalents.
* * * * *